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dc.contributor.authorChadegani, Alireza
dc.contributor.authorYang, Chihdar Charles
dc.contributor.authorDan-Jumbo, Eugene
dc.date.accessioned2019-03-08T22:07:03Z
dc.date.available2019-03-08T22:07:03Z
dc.date.issued2009-01
dc.identifier.citationChadegani, A., Yang, C., & Dan-Jumbo, E. (2008). Strain energy release rate analysis of adhesive-bonded composite joints with a prescribed interlaminar crack. Paper presented at the Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
dc.identifier.issn0021-8669
dc.identifier.issn1533-3868 (online)
dc.identifier.urihttp://dx.doi.org/10.2514/1.37513
dc.identifier.urihttp://hdl.handle.net/10057/15863
dc.descriptionClick on the DOI link to access the article (may not be free).
dc.description.abstractDelamination is among the critical failure modes in fiber-reinforced laminated composite structures. This paper presents an analytical approach by taking into account the first-ply failure in adhesive-bonded composite joints subjected to axial tension. The ASTM D3165 standard test specimen geometry is followed for model development derivations. The field equations, in terms of displacements within the joint, are formulated by using the first-order, shear-deformable, laminated plate theory together with kinematics relations and force equilibrium conditions. The stress distributions for the adherends and adhesive are determined after the appropriate boundary and loading conditions are applied and the equations for the field displacements are solved. The equivalent forces at the tip of the prescribed interlaminar crack are obtained based on interlaminar stress distributions. The strain energy release rate of the crack is then determined by using the virtual crack closure technique (VCCT). The system of second-order differential field equations is solved to provide the adherend and adhesive stresses using the symbolic computation tool, Maple 9.52. Finite element analyses using the J-integral as well as the VCCT are performed to verify the developed analytical model. Finite element analyses are conducted using the commercial finite element analysis software ABAQUS 6.5-1. Results are determined using the analytical method correlated properly with the results from the finite element analyses.
dc.language.isoen_US
dc.publisherAmerican Institute of Aeronautics and Astronautics
dc.relation.ispartofseriesJournal of Aircraft
dc.relation.ispartofseriesv.46 no.1
dc.subjectFinite element method
dc.subjectBoundary conditions
dc.subjectComposite structures
dc.subjectCrack closure
dc.subjectCrack propagation
dc.subjectCracks
dc.subjectDifference equations
dc.subjectDynamics
dc.subjectEnergy release rate
dc.subjectFailure analysis
dc.subjectFiber optics
dc.subjectImage segmentation
dc.subjectJoints (structural components)
dc.subjectLaminated composites
dc.subjectLaminating
dc.subjectQuality assurance
dc.subjectReliability
dc.subjectStandardization
dc.subjectStandards
dc.subjectStrain energy
dc.subjectStrain rate
dc.subjectStress concentration
dc.subjectStresses
dc.subjectStructural dynamics
dc.subjectStructure (composition)
dc.titleStrain energy release rate analysis of adhesive-bonded composite joints with a prescribed interlaminar crack
dc.typeArticle
dc.rights.holderCopyright 2008 by the American Institute of Aeronautics and Astronautics, Inc.


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